Aeroplane equipped with an internal escape hatch having a double opening controller

ABSTRACT

An aeroplane includes an escape opening passing through an external skin and an internal bulkhead. The escape opening is closed off by an external escape hatch having an external opening controller. The aeroplane further includes an internal escape hatch that closes off said escape opening flush with the internal bulkhead, and kept closed by at least one catch movable between a locked state and unlocked state, a first opening controller that controls the passage from the locked state to the unlocked state of the catch being accessible from inside the aeroplane, and a second opening controller that controls the passage from the locked state to the unlocked state of the catch being positioned such that the actuation of the external opening controller of the external escape hatch or the passage of the external escape hatch from the closed position to the open position causes the second opening controller to be actuated.

FIELD OF THE INVENTION

The present invention relates to an aeroplane equipped with an internalescape hatch having a double opening controller.

BACKGROUND OF THE INVENTION

As illustrated in FIG. 2, an aeroplane comprises a skin 10 that formsthe fuselage, a passenger cabin (not shown) delimited by an internalbulkhead, and a pilot cabin 12 delimited by an internal bulkhead 14.Various components are disposed between the skin 10 and the internalbulkhead 14, for example insulation blankets 16.

In order to evacuate the passengers and/or the pilots, the aeroplanecomprises an opening 18 for bringing the inside of the cabin 12 intocommunication with the outside 20 of the aeroplane, and at least oneescape hatch 22 for closing off or freeing the opening 18. According toan example that is visible in FIG. 1, this escape hatch 22 is positionedin the upper part of the fuselage, vertically above the pilot cabin 12.This escape hatch 22 comprises a wall having an external surface 24flush with the external surface of the skin 10 of the fuselage. Thisescape hatch 22 comprises locking/unlocking means 25 that are controlledby an internal opening controller 26 that is actuable from inside thefuselage, and by an external opening controller 28 that is actuable fromoutside the fuselage. Inside the fuselage, at the opening 18, it isnecessary to provide a lining element 30 in the opening 18 against theescape hatch in order to ensure the continuity of the internal bulkhead14 of the cabin 12.

This lining element 30 should be secured correctly in order not to fallaccidentally. However, it should be able to be removed rapidly in theevent of an emergency evacuation, in order to allow access to the escapehatch 22 from the inside. According to another constraint, it should bepossible to remove this lining element 20 with one hand.

Finally, in the event of intervention from the outside, it should bepossible to remove the lining element 30 from the outside.

Thus, the present invention proposes a solution that aims to meet atleast these constraints.

BRIEF SUMMARY OF THE INVENTION

To this end, a subject of the invention is an aeroplane comprising anexternal skin and an internal bulkhead delimiting a cabin, andcomprising an escape opening passing through said external skin and saidinternal bulkhead, said escape opening being closed off by an externalescape hatch that is movable between a closed position, in which it isdisposed flush with the external skin, and an open position, saidexternal escape hatch comprising locking/unlocking means that arecontrolled by an external opening controller, characterized in that theaeroplane comprises:

an internal escape hatch that closes off said escape opening flush withthe internal bulkhead,

at least one catch that is movable between a locked state and anunlocked state, said catch keeping said internal escape hatch in aclosed position in the locked state,

a first opening controller that controls the passage from the lockedstate to the unlocked state of the catch being accessible from insidethe aeroplane,

a second opening controller that controls the passage from the lockedstate to the unlocked state of the catch being positioned such that theactuation of the external opening controller of the external escapehatch or the passage of the external escape hatch from the closedposition to the open position causes the second opening controller to beactuated.

According to an embodiment of the invention, the internal escape hatchmakes it possible to close the escape opening at the internal bulkhead.By virtue of the catch, this internal escape hatch is kept in the closedposition in a reliable manner. Finally, this internal escape hatchcomprises a double controller for opening said hatch from the inside ofthe aeroplane but also from the outside.

Advantageously, the second controller comprises a pivoting lever, and acable which connects said lever to the catch, said lever and said cablebeing configured such that, during the actuation of the external openingcontroller of the external escape hatch or during the passage of theexternal escape hatch from the closed position to the open position, thelever pivots and exerts a traction force on the cable, causing the catchto pass from the locked state to the unlocked state.

According to another feature, the internal escape hatch comprises atleast one return means which causes the catch to tilt into the unlockedstate, and at least one locking handle that is movable between a firstposition corresponding to the locked state of the catch, in which thelocking handle immobilizes the catch counter to the one or more returnmeans, and a second position in which the locking handle does notimmobilize the catch, which tilts into the unlocked state by virtue ofthe one or more return means.

According to another feature, the internal escape hatch comprises atleast one return means for keeping the locking handle in the firstposition.

Preferably, the catch comprises at least one arm fixed to a shaft thatpivots about a rotation axis with respect to a holder connected to theinternal escape hatch, said rotation axis and the arm being configuredsuch that in the locked state, the arm or an element carried by the armis in contact with a stop, and such that in the unlocked state, the armor an element carried by the arm is spaced apart from the stop andallows the internal escape hatch to be opened. According to oneembodiment, the shaft comprises at least one notch and the lockinghandle comprises at least one protrusion which bears against the notchof the shaft in the locked state.

According to another feature, the locking handle is able to rotate abouta rotation axis and comprises a controller that is spaced apart from therotation axis by a distance greater than the protrusion(s).

Preferably, the cable of the second controller is connected to thelocking handle.

According to another feature, the internal escape hatch comprisespressure regulating means which automatically trigger the opening ofsaid internal escape hatch when a pressure difference on either side ofsaid hatch exceeds a given value.

Advantageously, the internal escape hatch is connected to the aeroplaneby at least one strap which comprises a ring, and the shaft whichsupports the catch comprises, for each strap, a hook having an end whichbears against a bearing surface when the catch is in the locked stateand which is spaced apart from said bearing surface when the catch is inthe unlocked state, the hook passing through the ring in the lockedstate.

BRIEF DESCRIPTION OF THE DRAWINGS

Further features and advantages will become apparent from the followingdescription of the invention, said description being given purely by wayof example, with reference to the appended drawings, in which:

FIG. 1 is a perspective front view of an aeroplane, illustrating anexternal escape hatch,

FIG. 2 is a schematic section through an escape opening, illustratingthe prior art,

FIG. 3A is a schematic section through an escape opening, illustratingthe invention,

FIG. 3B is a section illustrating a detail of FIG. 3A,

FIGS. 4A to 4C are diagrams which illustrate the principle of operationof an internal escape hatch that is actuated from the inside,

FIG. 5 is a perspective view from the outside of an internal escapehatch, illustrating one embodiment of the invention,

FIG. 6 is a section through a control mechanism for the movement of acatch illustrated in FIG. 5,

FIG. 7 is a perspective view which illustrates in detail the controlmechanism for the movement of the catch,

FIG. 8 is a perspective view of a first disconnect of hinge,illustrating one embodiment of the invention,

FIG. 9 is a perspective view of a second disconnectable hinge,illustrating one embodiment of the invention,

FIG. 10 is a diagram which illustrates the principle of operation of aninternal escape hatch that is actuated from the outside,

FIG. 11 is a perspective view which illustrates in detail a lever thatis actuable by way of an external opening controller for an externalescape hatch,

FIG. 12 is a perspective view which illustrates in detail the controlmechanism for the movement of the catch when it is actuated from theoutside,

FIG. 13 is a diagram which illustrates depressurization of a pilot cabinof an aeroplane,

FIGS. 14A and 14B are sections through the control mechanism for themovement of the catch during depressurization of a pilot cabin,

FIG. 15 is a front view which illustrates the internal escape hatchafter opening on account of depressurization of the pilot cabin,

FIG. 16 is a perspective view which illustrates in detail a centring pinthat is used to position the internal escape hatch,

FIGS. 17A and 17B are views of the external face of an internal escapehatch before and after an overpressure in the pilot cabin,

FIG. 18 is a side view of the water-absorbing element,

FIG. 19 is a perspective view of a lug for holding an overpressure panelof an internal escape hatch,

FIG. 20 is a perspective view of a holder for a permanent magnet of anoverpressure panel of an internal escape hatch, and

FIG. 21 is a perspective view of a permanent magnet of an overpressurepanel of an internal escape hatch.

DETAILED DESCRIPTION

FIG. 3A shows a part of an aeroplane which comprises a fuselage with anexternal skin 40 attached to a structure 42, and, inside the fuselage, acabin 44 delimited by an internal bulkhead 46 spaced apart from the skin40.

As illustrated in FIG. 13, an aeroplane comprises a pilot cabin 44provided at the front and a passenger cabin 44′ behind the pilot cabin44, separated from the latter by a separating bulkhead 47 whichcomprises a door for bringing the cabins 44, 44′ into communication.

Each cabin 44, 44′ is delimited by an internal bulkhead 46. Variouselements are interposed between the skin 40 and the internal bulkhead46, such as insulation blankets, for example.

According to an embodiment that is illustrated in FIG. 3A, the aeroplanecomprises at least one escape opening 48, which makes it possible tobring the inside of a cabin 44 into communication with the outside ofthe aeroplane and which opens out at the skin 40 forming the fuselageand at the internal bulkhead 46 of the cabin 44. Preferably, thisinternal bulkhead 46 extends, at least around the escape opening 48,approximately parallel to the skin 40 and at a distance from this skin.In one installation, the escape opening 48 leads onto the upper part ofthe fuselage. It is preferably positioned above the seat of the thirdoccupant of the pilot cabin 44 or not quite vertically above this seat,as shown in FIG. 15. This installation is preferred since it affordsbetter accessibility from the various positions on the pilot cabin.

For the rest of the description, as indicated in FIG. 1, a longitudinaldirection DL corresponds to the direction which extends from the fronttip to the rear tip of the aeroplane. A transverse plane is a planeperpendicular to the longitudinal direction. A radial direction DR is adirection perpendicular to the longitudinal direction.

In one configuration, the escape opening 48 is delimited by a perimetercomprising a front edge comprised in a first transverse plane, a rearedge comprised in a second transverse plane, a lower edge and an upperage parallel to the longitudinal direction and rounded portionsconnecting the front, rear, lower and upper edges.

However, the invention is not limited to this geometry for the perimeterof the opening.

The escape opening 48 is closed off by a removable external escape hatch50 flush with the skin 40, said external escape hatch 50 having ageometry adapted to that of the escape opening 48 and comprising a wallwith an external surface 52 flush with the external surface of the skin40 of the fuselage when the external escape hatch 50 closes off theescape opening 48. The external escape hatch 50 compriseslocking/unlocking means 54 that are controlled by an internal openingcontroller 56 that is actuable from inside the fuselage and by anexternal opening controller 58 that is actuable from outside thefuselage.

According to an embodiment illustrated in FIG. 10, the external escapehatch 50 is connected to the rest of the fuselage of the aeroplane by apivot pin 60. When the locking/unlocking means 54 are in the unlockedstate, the external escape hatch 50 can pivot about the pivot pin 60towards the inside of the fuselage.

In another embodiment, the external escape hatch 50 carries an elementwhich is moved towards the inside of the fuselage when the externalopening controller 58 is actuated.

The external escape hatch 50 is not described further, since it can beidentical to that of the prior art.

According to one feature of the invention, the aeroplane comprises, atthe escape opening 48 and the internal bulkhead 46, an internal escapehatch 68 that is movable between a closed position, in which it closesoff the escape opening 48, and an open position, in which it frees theescape opening 48. The internal escape hatch 68 comprises a rigid orsemi-rigid panel 69 having an internal surface 70 disposed flush withthe internal surface of the bulkhead 46 in the closed position, and anexternal surface 72 oriented towards the external escape hatch 50.

In one configuration, the aeroplane comprises a frame 74 which surroundsthe escape opening 48 and which cooperates with the internal escapehatch 68, the periphery of which coincides with that of the frame 74, soas to obtain leaktightness between the frame 74 and said internal escapehatch 68. This frame 74 comprises an upper edge 76 and a lower edge 76′that are approximately parallel to the longitudinal direction, and alsoa rear edge 78 in one transverse plane and a front edge 78′ in anothertransverse plane.

Preferably, as shown in FIG. 3B, the internal escape hatch 68 has shapescomplementary to those of the frame 74 so as to limit the movement ofthe internal escape hatch 68 in the radial direction DR towards theoutside of the aeroplane and to allow movements of the internal escapehatch 68 towards the inside of the aeroplane, on account in particularof the weight of the internal escape hatch 68.

According to one embodiment, the internal escape hatch 68 comprises alip 80 which prolongs the internal surface 70 of said hatch 68 and whichforms a contact surface 82 that is approximately perpendicular to theradial direction DR and bears against the frame 74 or the internalbulkhead 46 in the closed position. In addition, the frame 74 or theinternal bulkhead 46 comprises an indentation 84 having a contactsurface 86 against which the lip 80 bears when the internal escape hatch68 is in the closed position, said indentation 84 being dimensioned tohouse the lip 80 and such that the internal surface 70 of the internalescape hatch 68 is flush with the internal surface of the bulkhead 46.According to one embodiment, the lip extends around the entire peripheryof the internal escape hatch 68.

In one configuration, the internal escape hatch 68 has shapescomplementary to those of the frame 74 or the internal bulkhead 46 so asto help the centring thereof with respect to the frame 74 or theinternal bulkhead 46.

According to one embodiment, the internal escape hatch 68 has aperipheral edge face 88 in the form of a truncated pyramid, which helpsin centring (visible in FIGS. 3B and 17A).

The internal escape hatch 68 comprises at least one catch 90 configuredto take up a locked state in which the catch 90 keeps said internalescape hatch 68 in the closed position, and an unlocked state in whichthe catch 90 allows said internal escape hatch 68 to be opened, inparticular under the effect of gravity.

In the locked state, the catch 90 cooperates with at least one stop 92carried by the frame 74.

In one configuration, the stop 92 is positioned on the upper edge 76 ofthe frame 74, equidistantly from the rear and front edges 78, 78′. Thestop 92 protrudes with respect to the upper edge 76 and extends towardsthe lower edge 76′ approximately perpendicularly to the longitudinaldirection DL and to the direction DR.

The stop 92 is positioned with respect to the catch 90 so as to preventthe internal escape hatch 68 from moving when said catch 90 is in thelocked state. According to the embodiment, the stop 92 is positionedunder the catch 90 (offset towards the inside of the cabin) when thelatter is in the locked state.

Regardless of the embodiment, the structure of the aeroplane comprises,for each catch 90, at least one stop 92 which immobilizes the catch 90in a radial direction DR towards the inside of the aeroplane.Advantageously, the structure of the aeroplane comprises two stops, afirst stop 92 which immobilizes the catch 90 in a radial direction DRtowards the inside of the aeroplane and a second stop which immobilizesthe catch 90 in a radial direction towards the outside of the aeroplane.According to one embodiment, the second stop corresponds to the contactsurface 86 of the indentation 84 of the frame 74 or of the internalbulkhead 46.

Although it is described with a single catch, the internal escape hatch68 may comprise a plurality of catches, each of which is associated withat least one stop.

Preferably, the catch 90 is able to rotate with respect to a rotationaxis 94 approximately parallel to the longitudinal direction DL and tothe direction DR. To this end, the internal escape hatch 68 comprises apivoting connection with a rotation axis 94 for connecting the catch 90to the panel 69 of the internal escape hatch 68, the rotation axis 94being at a distance from the stop 92.

According to one embodiment, the connection between the catch 90 and thepanel 69 comprises on the one hand a holder connected to the internalescape hatch 68 in the form of a yoke 96 having two cylindrical bearingsurfaces 96 a and 96 b with coaxial axes coincident with the rotationaxis 94, and on the other hand a shaft 98 which pivots in the twocylindrical bearing surfaces 96 a and 96 b and to which the catch 90 isconnected.

The catch 90 comprises at least one arm 100 that is perpendicular to therotation axis 94 and fixed rigidly to the shaft 98. The rotation axis 94and the arm 100 are configured such that in the locked state, the arm100 or an element carried by the arm is in contact with the stop 92, andin the unlocked state, the arm 100 or an element carried by the arm isspaced apart from the stop and allows the internal escape hatch 68 to beopened.

According to one embodiment, the catch 90 pivots about the rotation axis94, in the anticlockwise direction, through an angle of around 120°between the locked state and the unlocked state.

According to an embodiment that is visible in FIG. 7, the catch 90comprises two parallel arms 100. Advantageously, the catch 90 comprisesat its end a roller 102 which is designed to roll on the stop 92.According to one embodiment, the two arms 100 carry at their free endsan axle on which the roller 102 is mounted in a pivoting manner.

Of course, the invention is not limited to these dynamics for the catch90. Instead of pivoting, the catch could move in translation between afirst position in contact with the stop 92, which corresponds to thelocked state, and a position spaced apart from the stop 92, whichcorresponds to the unlocked state. However, the embodiment illustratedin the figures is preferred, since the rotation of the catch 92 about arotation axis 94 makes it possible to obtain a lever effect.

The internal escape hatch comprises at least one mechanism forcontrolling the movement of the catch 90.

Preferably, this mechanism comprises at least one return means whichcauses the catch 90 to tilt in the unlocked state. According to oneembodiment, the mechanism for controlling the movement comprises twosprings 104, 104′ around the shaft 98, which cause the catch 90 torotate in the unlocked state.

In addition to the one or more return means 104, 104′, the mechanismcomprises at least one locking handle 106 which immobilizes the catch 90in the locked state, counter to the one or more return means 104, 104′.

According to an embodiment that is visible in FIGS. 6 and 7, the shaft98 comprises at least one collar 107 having at least one notch 108 atits periphery. This notch 108 has a contact surface passing through therotation axis 94. Preferably, the shaft 98 comprises two collars 107,107′ that are disposed in a symmetrical manner with respect to the catch90, each of said collars 107, 107′ comprising a notch 108.

In addition, the locking handle 106 comprises at least one protrusion110, one for each notch 108.

Preferably, the locking handle 106 is able to rotate about a rotationaxis 112 between:

a first position corresponding to the locked state of the catch 90, inwhich the locking handle 106 prevents the catch 90 from rotating, theprotrusion 110 of the locking handle 106 bearing against the notch 108of the shaft 98, and

a second position, in which the locking handle does not prevent thecatch 90 from rotating, the protrusion 110 being spaced apart from thenotch 108 of the shaft 98.

Preferably, the rotation axis 112 is parallel to the rotation axis 94 ofthe catch 90.

According to one embodiment, the locking handle 106 is connected to thepanel 69 by a pivoting connection which comprises:

a yoke 114 connected to the panel 69 with two cylindrical bearingsurfaces 114 a and 114 b having coaxial axes coincident with therotation axis 112,

a shaft 116 forming part of the locking handle 106 or connected to thelatter, which pivots in the two cylindrical bearing surfaces 114 a and114 b.

Preferably, the yokes 96 and 114 form a single assembly.

According to one embodiment, the locking handle 106 also comprises theshaft 116, two mutually parallel arms 118, 118′ that are perpendicularto the rotation axis 112, and a controller 120 in the form of a bar, thearms 118, 118′ connecting the shaft 116 and the controller 120, the arms118, 118′ each being disposed in line with a notch 108 and comprising aprotrusion 110.

At least one return means makes it possible to keep the locking handle106 in the first position in which it prevents the catch 90 fromrotating. According to one embodiment, two springs 123 are used asreturn means.

According to one configuration, the arms 118, 118′ carrying theprotrusions 110 are offset towards the inside of the aeroplane withrespect to the rotation axis 94. Thus, a traction force F towards theinterior of the aeroplane that is exerted on the controller 120 causesthe locking handle 106 to rotate, thereby freeing the catch 90, thelatter pivoting into the unlocked state on account of the one or morereturn means 104, 104′.

The invention is not limited to these dynamics for the locking handle106. Thus, instead of pivoting, the locking handle 106 could move intranslation. However, the variant with a rotational movement about therotation axis 112 makes it possible to obtain a lever effect, thecontroller 120 being spaced apart from the rotation axis 112 by agreater distance than the protrusion(s) 110.

The one or more return means 104, 104′ which cause the catch 90 to tiltinto the unlocked state make it possible to separate the force necessaryfor causing the catch 90 to tilt from the force to be applied to thecontroller 120 in order to cause the locking handle 106 to rotate.

Thus, the invention makes it possible to reduce the traction force Fexerted on the controller 120 in order to cause the change of state ofthe catch 90 and to cause the internal escape hatch 68 to open.

According to another feature of the invention, the passage of the catch90 from the locked states of the unlocked state is controlled by twocontrollers, a first opening controller that is accessible from insidethe aeroplane and a second opening controller that is connected to theexternal opening controller 58 of the external escape hatch 50, therebymaking it possible to trigger the opening of the internal escape hatch68 from outside the aeroplane.

The first opening controller comprises the catch 90 and locking handle106 described above. They are disposed between the two hatches 50 and68. Consequently, the panel 69 of the internal escape hatch 68 comprisesan opening 122 for making the controller 120 accessible from inside thecabin.

Thus, as illustrated in FIGS. 4A to 4C, in order to open the internalescape hatch 68, a person should pass one hand through the opening 122and then pull on the controller 120.

The second opening controller is situated between the external hatch 50and the internal escape hatch 68. It is positioned such that theactuation of the external opening controller 58 of the external escapehatch 50 or the passage of the external escape hatch 50 from the closedposition to the open position causes the second opening controller to beactuated.

The second opening controller comprises a lever 124 connected to thelocking handle 106 by virtue of a cable 126.

According to an embodiment shown in FIGS. 10 and 11, the lever 124pivots about a rotary pin 128 secured to the panel 69 by way of a holder130 fixed to its external surface 72.

The lever 124 comprises a first end 132 positioned so as to be incontact with the external escape hatch 50 or an element carried by saidhatch when the external opening controller 58 of the external escapehatch 50 is actuated.

According to one embodiment, the cable 126 is secured to the second end134 of the lever, the first and second ends 132 and 134 of the leverbeing disposed on either side of the rotation axis 128, the first end132 being further away from the rotation axis 128 than the second end134 in order to obtain a lever effect.

The cable 126 and the lever 124 are arranged such that when the lever124 tilts, it exerts a traction force on the cable 126.

As indicated above, the cable 126 comprises a first end connected to thelever 124 and a second end connected to the locking handle 106.

According to an embodiment illustrated in FIGS. 11 and 12, the cable 126is inserted into a sleeve 135 which comprises a first end that is lockedby a first holder 136 secured to the panel 69 and close to the lockinghandle 106, and a second end locked by a second holder 138 secured tothe panel 69 and close to the lever 124. At the exit from the second endof the sleeve 135, the cable 126 is parallel to the rotation axes 94 and112, in line with the controller 120. The panel 69 comprises a turnelement 140 so as to orient the cable 126 in a direction perpendicularto the rotation axes 94 and 112 and to the controller 120. Preferably,the locking handle 106 comprises a lug 142 disposed at one end of thecontroller 120 and perpendicular thereto, the cable 126 being connectedto said lug 142.

At the exit from the first end of the sheet 135, the cable 126 isoriented parallel to the rotation axis 128 of the lever 124. The panel69 comprises a turn element 144 for orienting the cable perpendicularlyto the rotation axis 128 of the lever 124 in the pivoting plane of thelever 124.

As illustrated in FIGS. 10 to 12, when the external opening controller58 of the external escape hatch 50 is actuated, the external escapehatch 50, or an element carried by said hatch, exerts a force on thefirst end 132 of the lever 124. As a result of this force, the lever 124pivots as illustrated in FIG. 10. The pivoting of the lever 124 causes atraction force on the cable 126, as illustrated in FIG. 11. The tractionforce exerted at the first end of the cable 126 is converted at thesecond end of the cable into a traction force on the locking handle 106,which pivots. By pivoting, the locking handle 106 frees the catch 90,which pivots into the unlocked state. The internal escape hatch 68 isthen open.

The second opening controller for controlling the passage of the catchfrom the locked state to the unlocked state is not limited in thisembodiment. Regardless of the variant, the second opening controllercomprises a lever 124 that is actuable by the external escape hatch 50and connected to the catch 90, the pivoting of the lever 124 during theopening of the external escape hatch 50 causing the catch 90 to passfrom the locked state to the unlocked state.

In one configuration, the upper edge 76 of the frame 74 comprises a stop92 which cooperates with a catch 90 secured to the panel 69 of theinternal escape hatch 68. In addition, the panel 69 comprises twodisconnectable hinges at the lower edge 76′. Each disconnectable hingecomprises a finger 146 which engages with a housing 148 provided at therear edge 76′ of the frame 74, as illustrated in FIGS. 5, 8 and 9.

As shown in detail in FIG. 8, each finger 146 comprises, at a first end,a mounting plate 148 fixed to the panel 69 and, at the other end, acylindrical form 150 (visible in FIG. 9) having an axis 152 parallel tothe rotation axis 94 of the catch 90. At least one housing comprises twoside walls 154, 154′ which prevent movement in translation in adirection parallel to the axis 152 of the cylindrical form 150 of thefinger 146.

Thus, in order to be able to release the internal escape hatch 68 of theopening, it is appropriate, firstly, to tilt the catch 90 into theunlocked state so as to allow said hatch to pivot slightly about theaxis 152 of the cylindrical forms 150, which then carry out the functionof hinges. By continuing, as illustrated by the arrows 156 in FIGS. 8and 9, the fingers 146 are disengaged from their housings 148.Consequently, the internal escape hatch 68 is opened and releases theescape opening 48.

According to another feature, the internal escape hatch 68 carries outthe function of pressure regulator and opens automatically when apressure difference on either side of the internal escape hatch 68exceeds a given value. To this end, it comprises pressure regulatingmeans which automatically trigger the opening of said internal escapehatch 68 when a pressure difference becomes too high on either side ofsaid hatch 68.

Thus, according to a first function, the internal escape hatch 68automatically opens in the event of depressurization of the pilot cabin44, as shown in FIG. 13.

To this end, the stop 92 is retractable. As illustrated in FIGS. 6, 14Aand 14B, the stop 92 is movable between a protruding positionillustrated in FIG. 6, in which it retains the catch 90 and prevents theinternal escape hatch 68 from being opened, and a retracted position,illustrated in FIG. 14A, in which it no longer retains the catch 90 andallows the internal escape hatch 68 to be opened. According to oneembodiment, the stop 92 slides in a cylindrical bush 158 provided in theupper edge 76 of the frame 74, with a sliding axis A158 approximatelyperpendicular to the longitudinal direction DL and to the direction DR.

The stop 92 comprises a return means 160, for example a compressionspring, which pushes the stop 92 into the protruding position. Inparallel, the stop 92 and the bush 158 have complementary shapes inorder to prevent the movement in translation of the stop 92 when itreaches the protruding position.

The return means 160 is set depending on the pressure differencenecessary to cause automatic triggering of opening of the internalescape hatch 68. By way of example, in the embodiment shown, thepressure difference which triggers opening is between 6 and 9 millibars.

Advantageously, the stop 92 comprises a front face 162 having abevelled, inclined first surface 164 which makes it possible to converta crushing force of the catch 90 perpendicular to the sliding axis A158into a movement of the stop 92 along the sliding axis A158 counter tothe return means 160.

According to one embodiment, in a plane containing the directions DL andDR, the front face 162 is domed and comprises, in its upper part, theinclined first surface 164, against which the catch 90 bears in thelocked state, as illustrated in FIG. 6, a top 166 against which thecatch 90 bears as it passes from the locked state to the unlocked state,as illustrated in FIG. 14A, and, in its lower part, a second inclinedsurface 168, the inclined surfaces 164 and 168 being approximatelysymmetric with respect to the sliding axis A158. By way of example, thefirst inclined surface 164 forms an angle of around 60° with respect tothe sliding axis A158.

Preferably, the catch 90 comprise a roller 102 which comes into contactwith the stop 92 and which makes it possible to eliminate frictionbetween the catch 90 and said stop 92.

As shown in FIG. 13, each of the cabin 44 and 44′ is more or lessleaktight. If depressurization occurs in the pilot cabin 44, there is asudden and large pressure difference between the pilot cabin 44 and thepassenger cabin 44′. This pressure difference has an effect on eitherside of the internal escape hatch 68. Thus, as shown in FIG. 14A, thispressure difference generates forces f at the external surface 72, saidforces f pushing the internal escape hatch 68 towards the inside of thecabin. On account of the forces f, the catch 90 exerts on the stop 92 aforce G oriented in the direction DR towards the inside of the cabin.When this force G exceeds a threshold value, the stop 92 retracts and nolonger retains the catch 90, which passes into the unlocked state, asillustrated in FIG. 14B. The opening of the internal escape hatch 68makes it possible to re-establish the equilibrium between the two cabins44, 44′. In order to give an order of magnitude, the threshold value ofthe force G is around 218 N.

By virtue of the invention, it is possible, in some aeroplanes, toeliminate pressure regulating systems at the separating wall 47 or thedoor thereof, thereby reducing the on-board mass. In other aeroplanes,the invention makes it possible to supplement existing pressureregulating systems and thus to increase the effectiveness thereof.

According to another feature, the internal escape hatch 68 is connectedto the structure of the aeroplane and more particularly to the frame 74by at least one strap 170. According to one embodiment, the internalescape hatch 68 is connected to the upper edge 76 of the frame by twostraps 170, 170′.

This configuration makes it possible to avoid a situation in which theinternal escape hatch 68 injures the person sitting under the latterduring the automatic triggering of opening of the internal escape hatch68 in the event of depressurization of the pilot cabin, as illustratedin FIG. 15.

Advantageously, each strap 170 is connected to the escape hatch 68 by aconnection 172 which automatically breaks the link between said internalescape hatch 68 and each strap 170, 170′ when the catch 90 is in theunlocked state. Specifically, the straps 170, 170′ should not impede theopening of the internal escape hatch 68 when the opening thereof istriggered voluntarily by a person pulling on the controller 120.

Preferably, as visible in FIG. 7, each strap 170, 170′ comprises at itsend a ring 174. In addition, the shaft 98 which holds the catch 90comprises, for each strap 170, 170′, a hook 176, the end of which bearsagainst a bearing surface 178 secured to the panel 69 when the catch 90is in the locked state. According to one embodiment, the yoke 96comprises two bearing surfaces 178, one for each strap, that areprovided on the outside of the cylindrical bearing surfaces 96 a, 96 b.Each hook 176 extends in a plane perpendicular to the rotation axis 94of the shaft 98, at each end of the shaft 98.

For each strap 170, 170′, in the locked state, the hook 176 passesthrough the ring 174 and retains it as long as its end is in contactwith the corresponding bearing surface 178. Thus, if the opening of theinternal escape hatch 68 is triggered on account of depressurization,with the catch 90 still remaining in the locked state, the straps 170,170′ remain secured to the internal escape hatch 68.

If the opening of the internal escape hatch 68 is triggered voluntarilyby a person pulling on the controller 120, then the locking handle 106frees the shaft 98, which can pivot. The rotation of the shaft 98 causesthe catch 90 to pass into the unlocked state and also frees the rings174, the ends of the hooks 176 being spaced apart from the bearingsurfaces 178.

Preferably, each bearing surface 178 comprises a pointed end that isinclined towards the inside of the cabin in order not to retain the ring174 when each hook 176 is spaced apart from the corresponding bearingsurface 178.

According to another function of pressure regulation, the internalescape hatch 68 makes it possible to regulate the pressure in the eventof over pressure in the pilot cabin 44.

To this end, the internal escape hatch 68 comprises an opening 180(visible in FIG. 17B) which makes it possible to bring the inside of thecabin 44 into communication with the intermediate region 182 (visible inFIGS. 3A and 13) between the internal bulkhead 46 and the skin 40 of thefuselage and an overpressure panel 184 configured to close off saidopening 180.

Advantageously, the overpressure panel 184 is as large as possible inorder that the pressure is distributed over as large a surface area aspossible.

Preferably, the opening 180 is at a distance from the peripheral edgeface 88 of the internal escape hatch 68.

According to one embodiment, the panel 69 of the internal escape hatch68 comprises two parts, a peripheral portion 186 which surrounds theopening 180 and a central portion which corresponds to the overpressurepanel 184.

The peripheral portion 186 comprises the opening 122 and carries theyokes 96 and 114, the lever 124 and the disconnectable hinges.

According to one embodiment, the opening 180 and the overpressure panel184 have the same rectangular peripheral shapes with rounded corners.

Advantageously, the overpressure panel 184 is connected to theperipheral portion 186 by a connection 188 which prevents any movementof the overpressure panel 184 towards the inside of the cabin 44 andwhich allows the overpressure panel 184 to move in the direction of theexternal escape hatch 50 when a force exerted on the overpressure panel184 in the direction of the external escape hatch 50 exceeds aparticular threshold.

The connection 188 comprises lugs 190 made of ferromagnetic materialthat are fixed to the external face 191 of the overpressure panel 184and which protrude from the periphery of said panel 184 so as to bepositioned above the peripheral portion 186. The connection 188 alsocomprises, for each lug 190, a holder 192 fixed to the external surface194 of the peripheral portion 186, and a magnetic element 196, such as apermanent magnet, for example, fixed to the holder 192, each magneticelement 196 being disposed under a lug 190. The magnetic force exertedby the magnetic elements 196 is adjusted depending on the desired valuefor the automatic triggering of opening of the overpressure panel in theevent of overpressure inside the cabin 44.

Thus, in the absence of overpressure, the lugs 190 bear against theholders 192 and prevent any movement of the overpressure panel 184towards the inside of the cabin 44. The magnetic elements 196 keep thelugs 198 pressed against their holders 192 and prevent any movement ofthe overpressure panel 184 towards the outside of the cabin 44. As soonas the overpressure inside the cabin 44 exceeds a particular threshold,the magnetic force of the magnetic elements 196 is insufficient toretain the lugs 190 and the overpressure panel 146 lifts so as to allowequalization of the pressures on either side of the internal escapehatch 68.

Advantageously, the secondary panel 184 comprises water-absorbingelements 198 at its external face 194. According to one embodiment,these water-absorbing elements 198 are in the form of strips that areadhesively bonded to the external face 194 of the overpressure panel 184and arranged so as to form a barrier configured to limit ingress ofwater into the pilot cabin 44, in particular during the descent phase offlights.

According to another feature, visible in FIG. 16, the internal escapehatch 68 comprises a centring means 200 for simplifying the positioningof said internal escape hatch 68 with respect to the structure of theaeroplane, and more particularly of the catch 90 with respect to thestop 92.

In order to position the upper edge 202 of the internal escape hatch, acentring pin 204 is fixed close to the upper edge 202, on the externalsurface 72 of said hatch. In addition, a plate 206 having an oblong slot208 is fixed to the structure of the aeroplane, more particularly to theframe 74. The oblong slot 208 has a width equal, allowing for play, tothe diameter of the centring pin 204 and its length is orientedsubstantially perpendicularly to the longitudinal direction DL and thedirection DR, in a direction parallel to the catch 90.

While at least one exemplary embodiment of the present invention(s) isdisclosed herein, it should be understood that modifications,substitutions and alternatives may be apparent to one of ordinary skillin the art and can be made without departing from the scope of thisdisclosure. This disclosure is intended to cover any adaptations orvariations of the exemplary embodiment(s). In addition, in thisdisclosure, the terms “comprise” or “comprising” do not exclude otherelements or steps, the terms “a” or “one” do not exclude a pluralnumber, and the term “or” means either or both. Furthermore,characteristics or steps which have been described may also be used incombination with other characteristics or steps and in any order unlessthe disclosure or context suggests otherwise. This disclosure herebyincorporates by reference the complete disclosure of any patent orapplication from which it claims benefit or priority.

The invention claimed is:
 1. An aeroplane comprising an external skin and an internal bulkhead delimiting a cabin, and comprising an escape opening passing through said external skin and said internal bulkhead, said escape opening being closed off by an external escape hatch that is movable between a closed position, in which the escape hatch is disposed flush with the external skin, and an open position, said external escape hatch comprising locking/unlocking means that are controlled by an external opening controller, the aeroplane further comprising: an internal escape hatch that closes off said escape opening flush with the internal bulkhead; at least one catch movable between a locked state and an unlocked state, said catch keeping said internal escape hatch in a closed position in the locked state; a first opening controller configured for controlling the passage from the locked state to the unlocked state of the catch being accessible from inside the aeroplane; a second opening controller configured for controlling the passage from the locked state to the unlocked state of the catch being positioned such that the actuation of the external opening controller of the external escape hatch or the passage of the external escape hatch from the closed position to the open position causes the second opening controller to be actuated; wherein the internal escape hatch comprises pressure regulating means which automatically trigger the opening of said internal escape hatch when a pressure difference on either side of said hatch exceeds a given value.
 2. The aeroplane according to claim 1, wherein the second controller comprises: a pivoting lever; and a cable connecting said pivoting lever to the catch, said pivoting lever and said cable being configured such that, during the actuation of the external opening controller of the external escape hatch or during the passage of the external escape hatch from the closed position to the open position, the pivoting lever pivots and exerts a traction force on the cable, causing the catch to pass from the locked state to the unlocked state.
 3. The aeroplane according to claim 2, wherein the locking handle is able to rotate about a rotation axis and comprises a controller that is spaced apart from the rotation axis by a distance greater than the protrusion(s), and wherein the cable is connected to the locking handle.
 4. The aeroplane according to claim 1, wherein the internal escape hatch comprises: at least one return means configured for causing the catch to tilt into the unlocked state; and at least one locking handle movable between a first position corresponding to the locked state of the catch, in which the locking handle immobilizes the catch counter to the one or more return means, and a second position in which the locking handle does not immobilize the catch, which tilts into the unlocked state by virtue of the one or more return means.
 5. The aeroplane according to claim 4, wherein the internal escape hatch comprises at least one return means for keeping the locking handle in the first position.
 6. The aeroplane according to claim 4, wherein the catch comprises at least one arm fixed to a shaft that pivots about a rotation axis with respect to a holder connected to the internal escape hatch, said rotation axis and the arm being configured such that in the locked state, the arm or an element carried by the arm is in contact with a stop, and such that in the unlocked state, the arm or an element carried by the arm is spaced apart from the stop and allows the internal escape hatch to be opened.
 7. The aeroplane according to claim 6, wherein the shaft comprises at least one notch and in that the locking handle comprises at least one protrusion which bears against the notch of the shaft in the locked state.
 8. The aeroplane according to claim 7, wherein the locking handle is able to rotate about a rotation axis and comprises a controller that is spaced apart from the rotation axis by a distance greater than the protrusion(s).
 9. The aeroplane according to claim 6, wherein the internal escape hatch is connected to the aeroplane by at least one strap.
 10. The aeroplane according to claim 9, wherein, in order to be connected to the internal escape hatch, each strap comprises a ring, and wherein the shaft which supports the catch comprises, for each strap, a hook having an end which bears against a bearing surface when the catch is in the locked state and which is spaced apart from said bearing surface when the catch is in the unlocked state, the hook passing through the ring in the locked state.
 11. The aeroplane according to claim 1, wherein the internal escape hatch comprises, at a first edge, a catch, and, at the opposite edge, two disconnectable hinges.
 12. The aeroplane according to claim 11, wherein the internal escape hatch comprises, at the first edge, a centering pin which engages with an oblong slot which is integral with the aeroplane and has a length parallel to the catch. 